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REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
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Journal of the Korean Society for Aeronautical & Space Sciences
Journal Basic Information
Journal DOI :
The Korean Society for Aeronautical & Space Sciences
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Volume & Issues
Volume 41, Issue 12 - Dec 2013
Volume 41, Issue 11 - Nov 2013
Volume 41, Issue 10 - Oct 2013
Volume 41, Issue 9 - Sep 2013
Volume 41, Issue 8 - Aug 2013
Volume 41, Issue 7 - Jul 2013
Volume 41, Issue 6 - Jun 2013
Volume 41, Issue 5 - May 2013
Volume 41, Issue 4 - Apr 2013
Volume 41, Issue 3 - Mar 2013
Volume 41, Issue 2 - Feb 2013
Volume 41, Issue 1 - Jan 2013
Selecting the target year
Aerodynamic Design of EAV Propeller using a Multi-Level Design Optimization Framework
Kwon, Hyung-Il ; Yi, Seul-Gi ; Choi, Seongim ; Kim, Keunbae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 3, 2013, Pages 173~184
DOI : 10.5139/JKSAS.2013.41.3.173
A multi-level design optimization framework for aerodynamic design of rotary wing such as propeller and helicopter rotor blades is presented in this study. Strategy of the proposed framework is to enhance aerodynamic performance by sequentially applying the planform and sectional design optimization. In the first level of a planform design, we used a genetic algorithm and blade element momentum theory (BEMT) based on two-dimensional aerodynamic database to find optimal planform variables. After an initial planform design, local flow conditions of blade sections are analyzed using high-fidelity CFD methods. During the next level, a sectional design optimization is conducted using two dimensional Navier-Stokes analysis and a gradient based optimization algorithm. When optimal airfoil shape is determined at the several spanwise locations, a planform design is performed again. Through this iterative design process, not only an optimal flow condition but also an optimal shape of an EAV propeller blade is obtained. To validate the optimized propeller-blade design, it is tested in wind-tunnel facility with different flow conditions. An efficiency, which is slightly less than the expected improvement of 7% predicted by our proposed design framework but is still satisfactory to enhance the aerodynamic performance of EAV system.
Computational Investigation of the Effect of Various Flight Conditions on Plume Infrared Signature
Kim, Joon-Young ; Chun, Soo-Hwan ; Myong, Rho-Shin ; Kim, Won-Cheol ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 3, 2013, Pages 185~193
DOI : 10.5139/JKSAS.2013.41.3.185
The plume infrared signature effects at various flight conditions of aircraft were investigated for the purpose of reducing infrared signature level. The nozzle of a virtual subsonic unmanned combat aerial vehicle was designed through a performance analysis. Nozzle and associated plume flowfields were first analyzed using a density-based CFD code and plume IR signature was then calculated on the basis of the narrow-band model. Finally, qualitative information for the plume infrared signature characteristics was obtained through the analysis of the IR signature effects at various flight conditions.
A Study on Stress Concentration Factor of Composite Laminate Mechanical Joints
Kwon, Jeong-Sik ; Kim, Jin-Sung ; Lee, Soo-Yong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 3, 2013, Pages 194~200
DOI : 10.5139/JKSAS.2013.41.3.194
In this paper, the results of composite laminate mechanical joints test(ASTM D5961) are compared with the theoretical strength calculations and FEM analysis results. To calculate the S.C.F.(stress concentration factor) on joint strength, equations on metallic and composite materials in ASM Handbook used and compared with experimental results. The difference of joint strength are compared by geometrical parameters and joining types(single/double lap joint). In FEM analysis, to find efficient FEM model on composite laminate mechanical joint, several FEM models are compared with experimental test results.
Roles of B-dot Controller and Failure Analysis for Dawn-dusk LEO Satellite
Rhee, Seung-Wu ; Kim, Hong-Joong ; Son, Jun-Won ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 3, 2013, Pages 200~209
DOI : 10.5139/JKSAS.2013.41.3.200
In this paper, the types of B-dot controller and the review results of B-dot controller stability are summarized. Also, it is confirmed that B-dot controller is very useful and essential tool when a dawn-dusk low earth orbit(LEO) large satellite has especially to capture the Sun for a required power supply in a reliable way after anomaly and that its algorithm is very simple for on-board implementation. New physical interpretation of B-dot controller is presented as a result of extensive theoretical investigation introducing the concept of transient control torque and steady state control torque. Also, the failure effect analysis results of magnetic torquers as well as a simulation verification are included. And the design recommendation for optimal design is provided to cope with the failure of magnetic torquer. Nonlinear simulation results are included to justify its capability as well as its performance for an application to a dawn-dusk LEO large satellite.
Individual Pitch Control of NREL 5MW Wind Turbine in a Transition Region
Nam, Yoonsu ; La, Yo Han ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 3, 2013, Pages 210~216
DOI : 10.5139/JKSAS.2013.41.3.210
Rotor blades experience mechanical loads caused by the turbulent wind shear and an impulse-like wind due to the tower shadow effect. These mechanical loads shorten the life of wind turbine. As the size of wind turbine gets bigger, a control system design for mitigating mechanical loads becomes more important. In this paper, individual pitch control(IPC) for the mechanical loads reduction of rotor blades in a transition wind speed region is introduced, and simulation results verifying IPC performance are discussed.
Analysis on Dynamic Characteristics and LQR Control of a Quadrotor Aircraft with Cyclic Pitch
Jo, Sungbeom ; Jang, Se-Ah ; Choi, Keeyoung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 3, 2013, Pages 217~225
DOI : 10.5139/JKSAS.2013.41.3.217
Typical quadrotor aircraft use four differential thrust vectors to control the motion. In this study, we design a quadrotor aircraft using collective and cyclic control to improve the shortcomings of existing quadrotor aircraft. The quadrotor aircraft with cyclic control can fly at various attitudes due to the excessive control degrees of freedom. Hence the quadrotor aircraft with cyclic control is suitable as high performance aircraft. In this study, modeling and stability analysis of the quadrotor aircraft have been performed using FLIGHTLAB. LQR control systems were designed using linear models at various flight conditions and verified through nonlinear simulations using MATLAB.
Fuel cell system for SUAV using chemical hydride - I. Lightweight hydrogen generation and control system
Hong, Ji-Seok ; Jung, Won-Chul ; Kim, Hyeon-Jin ; Lee, Min-Jae ; Jeong, Dae-Seong ; Jeon, Chang-Soo ; Sung, Hong-Gye ; Shin, Seock-Jae ; Nam, Suk-Woo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 3, 2013, Pages 226~232
DOI : 10.5139/JKSAS.2013.41.3.226
A compact hydrogen generation device of fuel cell system using chemical hydride storage technique was designed to fit the propulsion device requirement of a small unmanned aerial vehicle(SUAV). For high efficient, compact, and lightweight hydrogen generation control device, the Co-B catalyst hydrogen conversion rate by
aqueous solution flux is measured so that the proper amount of Co-B catalyst for maximum hydrogen generation of 100W stack was proposed. A compact hydrogen generation device is controlled by pump`s on/off using its own internal pressure and consumes fuel in high efficiency through a dead-end type fuel cell. The fuel cell system has stable operation for a planed flight profile. The system operates up to maximum 7 hours and at least 4 hours for tough flight profiles.
Fuel cell system for SUAV using chemical hydride - II. Lightweight fuel cell propulsion system
Hong, Ji-Seok ; Park, Jin-Gu ; Sung, Myeong-Hun ; Jeon, Chang-Soo ; Sung, Hong-Gye ; Shin, Seock-Jae ; Nam, Suk-Woo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 3, 2013, Pages 233~239
DOI : 10.5139/JKSAS.2013.41.3.233
A 100 W fuel cell system using chemical storage method has been applied for a propulsion system of the SUAV(Small Unmanned Aerial Vehicle). A fuel cell and battery have been combined for both the small/light hydrogen generation control system and the hybrid power supply system. A small hydrogen generation device was implemented to utilize NaBH4 aqueous solution and dead-end type PEMFC system, which were evaluated on the ground and by the flight tests. The system pressurized at a 45kpa stably operates and get higher fuel efficiency. The pressure inside of the hydrogen generation control system was maintained at between 45 kPa and 55 kPa. The 100W fuel cell system satisfies the required weight and power consumption rate as well as the propulsion system, and the fuel cell system performance was demonstrated through flight test.
Black Body Design and Verification for Non-Uniformity Correction of Imaging Sensor and Uncertainty Analysis
Shin, Somin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 3, 2013, Pages 240~245
DOI : 10.5139/JKSAS.2013.41.3.240
Each pixel of InfraRed(IR) sensor differently responds to IR light as time elapses or the sensor on/off operation is repeated. As a result, the quality of IR sensor image is deteriorated, and therefore NUC(Non-uniformity Correction) is periodically needed for IR sensor. In this paper, in order to perform NUC in the Satellite, on-board V-grooved blackbody is designed with a baffle so that the emissivity of black body is to be higher than 0.995 as well as the temperature deviation is less than
in the range of the infrared wave length from 3.3 to
. To check its performance, the emissivity and the surface temperature of the blackbody by TRT(Transfer Reference Thermometer) and IR Micrometer scanner are measured, respectively. From the results, black body design is verified and the uncertainty of NUC is estimated through the measurement results.
Filter design for protecting signal interference between RF equipments on aircraft
Kim, Junhyoung ; Kim, Bong-Gyu ; Jeon, Young-Gu ; Lee, Seong-Woo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 3, 2013, Pages 246~252
DOI : 10.5139/JKSAS.2013.41.3.246
This paper presents method to suppress signal interference by using the filter in the RF output stage of the radiation equipment as a way to avoid interference between the RF(Radio Frequency) equipment mounted on aircraft. Especially filter design to suppress harmonics of the radiation equipment and testing method to verify the filter`s performance is presented. Filter was installed at RF output stage of U/VHF radio in order to prevent interference between U/VHF(Ultra/Very High Frequency) radio and data link system. Filter design and testing method in this paper will be able to give help in the design of aircraft equipments as a tool that can be used to establish measures for problem of interference in the aircraft.